Compressor turbine



May 30, 1950 YQUHQUSE 2,509,555

COMPRESSOR TURBINE Filed Dec. 4, 1946 3 Sheets-Sheet 1 I HQ:

INVENTOR. JOSEPH YummusE Y ATTORNEY 3 Sheets-Sheet 2 J. YOUHOUSECOMPRESSOR TURBINE May 30,

Fil ed Dec. 4, 194a May 30, 1950 .1. YOUHOUSE COMPRESSOR TURBINE 3Sheets-Sheet 3 Filed Dec. 4, 1946 km Pm INVENTOR. JusBPH YZnmnusE ATTORNEY Patented May 30, 1950 s 'PATE NT, orr ca oomra'sssoa 'rmummJoseph Youhoule, l'alrileld, Conn. Application nmaw 4, 1m, Serial No.nasal "Claims. (on. re-41) This invention relates to new and usefulimprovements in power plants utilizing explosive ins] and has particularrelation to a compressor turbine.

An object or the invention is to provide a compressor turbineproviding-tor a relatively high compression ratio in a single stage.

Another object is to provide a compressor tunbine wherein the fuel iscompressed by centrifugal action and by a. further positive action priorto and at the time oi ignition.

Another object is to provide a compressor turtime so constructed as toprovide for centrifugal and positive displacement compression of the igases obtained inone stage by therelative movement of two rotatingelements. 7

An additional object is to provide a compressor turbine includingcentrifugal impellers for movement of the explosive gases to compressionand bring chambers.

Another object is to provide a turbine eompressor having the attributeof high thermal emciency because of the immediate impincins of thecombustion pressures on the turbine blades without excessive thermal andfrictional losses.

Yet another object is to provide a compressor turbine which will 0because the combustion gases act on the turbine blades during somewhatless than one-half of the rotatinaarc.

Yet another object is to provide a compressor turbine including a pairof rotating elements locked together by continually meshing star andinternal users and wherein the othercomponents while in extremelyslightly spaced relation are stationary casing perate at a safetemperature I not in mechanical contact whereby there is no mechanicalwear and the unit is tree or lubricating problems and is inherentlyquiet and has a low service requirement. c

Other objects and advantages of the'invention will become apparent froma consideration or the following detailed description taken inconnection with the accompanying drawings wherein a satisfactoryembodiment of the invention is shown. However, it is to be understoodthat the invention is not limited to the details disclosed but includesall such variations and modifications aetallwlthin the spirit of theinvention andthe scope of the appended claims.

In the drawings: 5 r

Fig. l is a side elevatlonal view looking at the exhaust side of anengine constructed in accordance with the invention;

Fig. 2 is an edge elevatlonal view of the engine;

2 Fig. 3 is a central vertical sectional view through the engine;

llig. 4 is a view looking the compression chamber element or the engine;

Fig. 5 is a somewhat similar view looking at the outer side of what maybe termed the piston elemental the engine;

Fla". 6 is a detail elevational view showing a portion or the element ofFig. 5 but looking from the opposite side thereof;

Fig. 'l is a developed view taken as along the line l-'l orFig. 8; p i

Fig. 8 is an enlarged detail sectional view takon as along the line 8--tof Fig. 4;

Fig. 9 is a detailed view in elevation show-ins the manner or mountingturbine blades on a ring or carrier; and

Fig. loisan elevatioual view suggesting a manner of forming the turbineblades.

Referring in detail to the drawings, my improved engine is shown asincluding an outer generally designated in and comprising asubstantially circular mid section l l, aclosure and bearing sectionside of the. section ll, as at l3, and a. closure and bearing section l4bolted to the other side of the mid section. as at l5. section may haveless or a base it secured thereto or integral therewith and adapted tobe bolted or otherwise fastened to any suitable support not shown). Theclosure and bearing member it may conveniently include an exhaustmanilold ll to which an exhaust pipe is is shown secured as by bolts 59.On their outer surfaces; the housing or casing parts II and it are shownas provided with heat dissipating vanes so.

into an open. side of or cylinder carryinl Within the casing or housingdescribed there 7 3i and 22 are secured to shafts 23 and ll, re

ntthrough a sleeve 2 secured to the cover member -j pectively.

' Shaft 21 is secured in element 2! and in; 26 provided a hub portion 2501' the passes outwardly through a bearin the cover member I! and then Iand an outer bearing means 28 located in a cylindrical hub Withparticular attention to Fig. 3, it will be noted that the shaft 23 islocated at an uncle to the horizontal and this is the permanent posil2bolted to one- At its lower side the mid qulpped with turbine blades andfully appear. Elements dike housing 2! I! .as by bolts 3|. I

tion of the shaft. Moreover, the'element 2| is located normal to theaxis of the shaft 23 whereby said element is at a slight angle to thevertical.

On the inner end of the hub 26 is a star gear 3|, the purpose of whichwillbe set forth. Ex

tending radially from said hub are a series of vanes or impellers 32relieved at their inner ends to clear the. gear 3|. hub, a wall 33 islocated over the outer edges of the vanes or impellers 32 and as shownis formed integral with them. This wall is in the nature of an annulusand at its inner periphery is turned outwardly as at 34 leaving a space35 between the hub and the wall for the entrance of a combustiblemixture admitted to the casing It as through an intake port 39 providedin the hub-like portion of the cover l2.

At the outer ends of or beyond the vanes 32, the wall 33 is carriedinwardly at a number of spaced points providing an annular series ofpistons 31 extending from the inner side of the element 2|,

towardthe outer edge of such element. The pistons 31 have their adjacentends in slightly spaced relation, the space between such ends beingindicated at 33 and being in the nature of pockets or recesses. Asherein shown, the pisdevice and effecting economy in the use ofmaterial. As best shown in Fig. 5, the vanes or impellers 32 areslightly offset from direct radial lines with respect to the hub 23.This is to provide for relative movement of such vanes or impellers atthe sides oi. vanes or impellers of the element 22 as will later fullyappear. I

The element 22 includes a hub portion 39 rigid with the inner end of theshaft 24 and such shaft extends outwardly through a bearing 49 locatedwithin a central portion of the cover member l4 and then through asleeve 4| and a bearing 42 located within a tubular housing 43 extendingcentrally and horizontally outwardly from the cover member I4 andsecured thereto as by bolts or the like 44. It is noted that the shaft24 is arranged horizontally and that the element 22 is normal to theshaft or vertical. Thus, the shaft 23 and its element 2| are arranged ina slightly oilset or angular relationship to the shaft 24 and itselement 22.

In addition to its hub-like portion 39, the element 22 includes aradially extending web-like portion 45 shown as concavo-convex intransverse section (see Fig. 3) and on its outer peripheral edgeprovided with a wall-like flange 46. On its forward side or on its sidetoward the element 2 I, the web-like portion 45 of element 22 isprovided with a series of vanes or impeller blades 41 includingextensions or extension-like portions 48 carried beyond the wall 46.

These extensions 48, together with the wall portion 46 and an inwardlydirected annular flange 49 carried by the casing section II and theportion of said casing section immediately forward oi said flange 49,define a series of cylinders or pockets 60 each of a size slightlygreater than the size of one of the pistons 31. It will be understoodthat as the flange 49 and, in fact, the entire casing section I I isstationary, that portion of the flange forming the outer portion of therear wall of any particular cylinder 50 and that portion of the outerannular wall of section II forming the outer limit of any particularcylinder is constantly changing when the engine is in operation as atsuch time the elements 2| and 22 are rotating with their shafts 23 and24.

In spaced relation to the v A series of bolts 3| serve to secure threerings 52, I3 and 34 in. a semi-nesting relation and to,

the wall or flange 43. Of these rings, the rings acting on the blades 56and 66. As these latter blades are driven by said products ofcombustion, the element 22 carrying such blades as well as the element2| is rotated.

The impeller blades or vanes 41 of the element 22 extend radially withrespect to the hub-like "tons are hollow thus reducing the weight of theportion 39 and laterally with respect to the weblike portion 43 of saidelement, and in the assembly, the relationshipoi' these blades orvanesto the blades or vanes 32 of element 2| is a side- 'by-side relation,although a close side-by-side renation. This is made apparent fromacomparison of Figs. 5, 6 and '1 as it is noted that the extensions 43of. the blades 41 are at certain times received in the recesses 33between the pistons 31. Such recesses are offset but slightly laterallyof the blades or vanes 32 and, in fact, one edge of each recess may besubstantially flush with one side or edge of a vane.

In the forward side of its hub portion 39, the element 22 is slightlyrecessed, as at 69. and against the outer annular wall of said recess,an internal ring gear 69 is flxed. This ring gear is of asize andconstruction to mesh with the star gear 3| carried on the hub portion ofthe element 2|. Due to this meshing oi the gears and to the relationshipof the vanes or blades 32 with the vanes or blades 41, the elements 2|and 22 rein the neighborhood of .010 inch and this is therelationshippreferably existing between the pistons 31 and thewalls of the cylindersor recesses 69.

As shown in the drawings, the firin position for each cylinder 50 andeach piston 31 is at the bottom of the engine. At the flring position, arecess 6| is provided in the flange 49 forming a slight enlargement of acylinder at this point and communicating with said recess is an ignitiondevice as the spark plug generally designated 32. As here shown, theelements 2| and 22 are designed to rotate in the direction indicated bythe arrow 63, in Fig. 4, and immediately beyond the .firing chamber, theWall or flange 49 is provided with a series of ports 64 preferablyarranged at an angle as shown in Fig. 7 and communicating the cylinders59, which at any given time are over said ports, with the turbineblades.

The hot expanding products of combustion passing through said portsfrom-the cylinders impinge upon the turbine blades to drive the sameforwardly togetherwith the entire element 22 and then impinging upon thestationary blades 61' are ll reversed and then impinge upon th blades 63to v assist in the forward driving of the element 22. Thereaftenas hereshown, such gases are exhausted into the manifold I1 and thence throughthe exhaust pipe it. However, it will be understood that additional setsof turbine rings and blades may be incorporated in the engine if that isdesired. r

Owing to the angular relationship of the shafts 23 and and of theelements 2| and 22, it will be a preciated that in the course ofrotation any given piston will be entirely out of its cylinder when saidpiston and its cylinder are at the top or upper side of the engine. Asthe elements rotate together and said piston and cylinder move downwardlalong the right side of the engine, as viewed in Fig. 4, the piston. bya constant movement, enters its cylinder until when said piston andcylinder reach the bottom or lower side of the engine, at the firingchamber, the piston has entered the cylinder to the maximum depthprovided for or to a point very close to the maximum depth provided for.Then, as rotation continues and that piston and cylinder move upwardlyalong the left hand side of the engine, as viewed in Fig. 4, the pistongradually shifts out of the cylinder until the point of maximumseparation is reached at or about the top or upper side of the engine.

With the foregoing in mind, the operation of the engine is readilyunderstood. For example, the proper fuel is fed in through the port 36and due to the rotation of the elements 2| and 22 there is a centrifugalaction tending to throw the fuel toward the outer periphery of theengine. This tendency is assisted by the vanes or impeller blades 32 and41 with the result that there is a slight compression of the fuel towardthe outer periphery of the engine and a slight compression of the fuelin any given cylinder atthe point of maximum withdrawal of the pistonfrom the cylinder. This insures a full charge to each cylinder. In fact,it is when a piston and cylinder are re- From the above it is thoughtthat it will be clear that a high compression ratio will be obtainedwith the present engine and that there is a certain compression of thefuel charge due to centrifugal action or the rotating parts and afurther compression as the pistons enter their cylinders. Thecentrifugal compression, as well cylinders. Owing to the angularrelationship of lated, as are those at the upper side of Fig. 3,

that the greater part of the charge enters the cylinder.

As the rotation progresses and th piston progressively enters acylinder, the charge therein is progressively compressed until the pointof maximum compression is reached at the firing station, or at the sparkplug 62. There, the explosion having taken place, the piston is notblown out of a cylinder but can only recede therefrom during the courseof the upward movement of the piston and cylinder over approximatelyone-half of the path of circular travel of these parts. .It is duringthis time that the hot expandlng gases from the cylinder, movingoutwardly through the ports 84, engage the various sets of vanes andoperating on the vanes and 56, impart rotative movement to such vanesand thus to the element 22.

As the element 2! is geared to the element 22 through the gears II andBI and through the overlapping relationship of the vanes or blades 32and H, it will be apparent that the rotatable movement of the element 22results in the identical movement of the element 2|. Owing to the highspeed at which the engine rotates, the slight clearance provided betweenany piston and the walls of its cylinder while admitting of the loss ofsome fuel during the compression, does not admit of the loss of amaterial portion of the charge. This is due to the slight clearanceprovided in combination with the rapidity of motion of the rotating theelement, the movement of the pistons into and out of the cylinders isobtained without the use of any actual mechanism. Because of theimmediate impinging of the combustion pressures on the turbine blades,the engine has a high thermal efficiency and owing to the employment ofthe numerous radiating vanes and to the fact that the combustion gasesact on the blades for somewhat less than one-half of the rotating arc,excessive temperatures in the parts is avoided.

As the two rotating elements 2| and 22 are locked together by thecontinuously meshing gears and the various portions of said elementsalways have a slight clearance. and are thus without mechanical contact,it will be clear that there is no reason for wear and that there are nolubricating problems in connection with the present unit which thereforehas a low service requirement and is inherently quiet.

While the ignition device 62 is shown as located at the bottom or lowerside of the engine,

it will be understood that the invention is not limited to thisarrangement. Device or spark plug 62 will, in any construction, belocated at a point of high compression and this will depend on therelation of element 2| to element 22.

For example, should the shaft 23 be arranged to incline instead of at adecline, the spark plug would be located toward the top or upper side ofthe engine. If the shaft is directed to one side or the otherof thevertical rather than the horizontal, the inlet and firing stations willbe at one side or, the other of the vertical rather than the horizontalcenter.

In fact, the piston construction or piston carrying element 2| might bearranged in a definite plane, as a definite vertical plane, and thecylinder construction or element 22 may be: arranged slightly off thevertical. This would be the reverse of what is shown and described butthe action or operation would be about the same. Preferably, anyparticular piston and its cylinder are beyond the end of the row ofports Bl prior to separation of such piston and cylinder for theadmission of a new fuel charge.

1 rings.

Figs. 9 and 10 suggest a manner in which the various -turbine blades maybe made and mounted on the various rings at little initial expense, aswithout the use of patterns and the like. The method consists in orcomprises the extruding orotherwise forming of a strip or continuouslength of stock of any desired size and of the proper transversecontour, as shown at 65 in Fig. 10. t

Then this stock is cut, as at 66, into suitable lengths 61. Each suchlength will comprise one turbine blade. Then these lengths or blades arewelded or otherwise rigidly secured to one of the For example, in Fig.9, the blades 56 are shown as welded at 68 to the ring 54. This samemethod or forming a length of stock of the proper transverse contour,cutting the stock into blade lengths, and then weldingthe blade lengthsin proper order to a, ring or other body is followed in connection withthe blades of the rings 53 and 52, as well as the ring 54.

Having thus set forth the nature of my invention, what I claim is:

1. In a compressor turbine, a stationary casing, a pair of shaftsrotatably mounted in said casing, a pair of rotatable elements in saidcasing and mounted on the respective shafts, means whereby said elementsrotate together as a unit, pistons carried by one of said elements,cylinders formed by the other of said elements, turbine blades carriedby one of said elements, a firing station, said piston carrying elementand its shaft mounted at an angle to the cylinder carrying element andits shaft whereby during a. portion of each revolution of the elementsas they approach said firing station said pistons are moved into thecylinders and during the remaining portion of each such revolution asthe elements are carried beyond the firing station said pistons aremoved out of the cylinders, and means for delivering the ignitedexpanding fuel charge from the cylinders to said turbine blades.

2. In a compressor turbine, a stationary casing, a pair of shaftsrotatably mounted in said casing, a pair of rotatable elements in saidcasing and mounted on the respective shafts, means whereby said elementsrotate together as a. unit, pistons carried by one of said elements,cylinders formed by the other of said elements, turbine blades carriedby one of said elements, a firing station, one of said elements and itsshaft mounted at an angle to the other element and its shaft wherebyduring a portion of each revolution of the elements as they approachsaid firing station the pistons and cylinders are progressivelytelescoped and during the remaining portion of each such revolution asthe elements are carried beyond said firing station the pistons andcylinders are progressively separated, and means for delivering theignited expanding fuel charges from the cylinders to said turbineblades.

5. In a compressor turbine, a casing. a pair of rotary elements in saidcasing, cylinder construotions at a side of one of said elements to wardits outer peripheral edge, pistons at a side of the other element towardits outer peripheral edge, means whereby said elements rotate together,means whereby as said elements rotate they are moved bodily relativelyand the pistons and cylinder constructions are progressively telescopedfor a portion of a revolution and are progressively separated for theremaining portion of the revolution, turbine blades fixed to one of saidelements, a fixed firing station, an ignition means at said station forigniting the fuel in the cylinders as they reach the station, and

means for impressing the expanding ignited 3. In a compressor turbine,an outer stationary casing having an outer wall portion and a centralhub portion, said casing having an inlet through said hub portion for afuel comprising a compressible explosive mixture, means within saidcasing and rotatable on an axis substantially concentric with said hubportion and by centrifugal action moving toward the outer portion ofsaid casing and compressing such an explosive mixture fed through saidinlet, means for thereafter further compressing the mixture by amechanical action, a rotatable element carrying turbine blades, meansfor igniting the fuel following compression by said mechanical action,and means for impressing the ignited charge on said turbine blades toimpart rotation to said element.

4. In a compressor turbine, a casing, a pair of rotary elements in saidcasing, cylinder constructions at a side of one of said elements towardits outer peripheral edge, pistons at a side of the other element towardits outer peripheral edge, means whereby said elements rotate together,and means whereby as said elements rotate they are moved bodilyrelatively and the pistons and cylinder constructions are progressivelytelescoped for a portion of a revolution and are progressively separatedfor the remaining portion of the revolution.

charge on said turbine blades to impart rotation to said elements.

6. In a compressor turbine, a casing, a pair of rotary elements in saidcasing, one of said elements having cylinder constructions at its outerperipheral edge, pistom at the outer peripheral edge of the otherelement, means whereby said elements rotate together, means for feedingfuel into said casing, means rotatable with said elements for impellingsaid fuel in a circular path within said casing as said elements arerotated whereby as said elements rotate said fuel is by centrifugalaction compressed at the outer peripheries of the elements, turbineblades fixed to, one of said elements, means whereby as said elementsrotate said piston and cylinder constructions are progressivelytelescoped for a portion of a revolution to further compress fuel insaid cylinder constructions, a firing station adjacent the point ofmaximum telescoping of said pistons and cylinder constructions, portsbeyond said firing station for delivering the ignited expanding fuelcharges from the cylinders to said turbine blades for impingement of theexpending products of combustion thereon to rotate the blades andelements, and said means for causing progressive telescoping of thepistons and cylinder constructions as they approach said firing stationoperative to progressively separate the pistons and cylinderconstructions as they recede from said station.

7. In a compressor turbine, a casing, a pair of rotary elements in saidcasing, one of said elements having cylinder constructions at its outerperipheral edge, pistons at the outer peripheral edge of the otherelement, means whereby said elements rotate together, means for feedingfuel into said casing, means rotatable with said elements for impellingsaid fuel in a circular path within said casing as said elements arerotated whereby as said elements rotate said fuel is by centrifugalaction compressed at the outer peripheries of the elements, turbineblades fixed to one of said elements, means whereby as said elementsrotate said piston and cylinder constructions are progressivelytelescoped for a portion of a revolution to further compress fuel insaid cylinder constructions, a firing station adjacent the point ofmaximum telescoping of said pistons and cylinder constructions, portsbeyond said firing station for delivering the ignited expanding fuelcharge from the cylinders to said turbine blades for impingement of theexpanding products of combustion thereon to rotate the blades andelements, said means for causing progressive telescoping of the pistonsand cylinder constructions as they approach said firing stationoperative to progressively separate the pistons and cylinderconstructions as they recede from said station, and said means in thislater action operative to fully separate the pistons and cylinderconstructions for the admission of fuel to the latter at a place remotefrom said firing station.

8. In a compressor turbine, a stationary casing, a cylinder carryingelement rotatably mounted in said casing, a piston element rotatablymounted in said casing, means whereby said elements must rotate as a,unit in said casing, an annular flange on said casing and forming aportion of a wall of each cylinder of said cylinder carrying element,turbine blades beyond said annular flange and secured to said cylindercarrying element, a firing station, means whereby the pistons andcylinders of the respective elements are progressively telescoped as therotation of the elements carries the pistons and cylinders toward saidfiring chamber and whereby said pistons and cylinders are progressivelyseparated as the elements carry them beyond said firing station, andports in said annular' flange in its portion beyond said firing stationfor impressing an ignited expanding fuel charge from the cylinders onsaid turbine blades.

9. In a compressor turbine, a stationary casing, a first elementrotatably mounted in said casing and having means at its outer peripheryfor cooperation with the casing to define a plurality of cylindersmovable with the element as the latter is rotated, a second elementrotatively mounted in said casing and at its outer periphery carrying aplurality of pistons for cooperation with said cylinders, means gearingsaid elements together for rotation as a unit, an annular flange on saidcasing and defining a portion of a wall of each of said cylinders,turbine blades at the outer side of said flange and fast to one of saidelements, a firing station, means whereby the respective pistons andcylinders of the elements are telescoped at said station and separatebeyond said station as said elements rotate, and ports in said flangebeyond said station and through which the ignited expanding products ofcombustion may escape from the cylinders and impinge on said turbineblades.

10. In a compressor turbine, a rotary means, turbine blades on saidmeans, said means comprising a pair of elements, means mounting saidelements in angularly related planes for rotation together and for arelative rocking movement, impellers on and movable with said means tocompress a fuel charge by centrifugal action, piston and cylinderconstructions on said means to thereafter further compress said fuelcharge by a positive mechanical compression, means to fire said charge,and means whereby the expanding ignited products of combustion areimpressed on said turbine blades.

11. In a compressor turbine, a, rotary multicylinder construction and arotary multi-piston construction, means positively connecting turbinebaldes to one of said constructions, means for compressing fuel bycentrifugal action and supplying it to the cylinders of said multiscylinder construction and thereafter mechanically compressing it bytelescoping of the respective cylinders and pistons of saidconstructions, means for firing the charges in the respective cylinderswhile the cylinders and pistons are telescoped at a predetermined placein the path of rotation of the constructions, and means for conductingthe expanding products of combustion Irom said cylinders to said blades.

12. In a compressor turbine, a rotary multicylinder construction and arotary multi-piston construction, means positively connecting turbineblades to one of said constructions, means for compressing fuel bycentrifugal action and supplying it to' the cylinders of saidmulticylinder construction and thereafter mechanically compressing it bytelescoping of the respective cylinders and pistons of saidconstructions, means for firing the charges in the respective cylinderswhile the cylinders and pistons are telescoped at a predetermined placein the path of rotation of the constructions ports for conducting theexpanding products of combustion from said cylinders to said blades, andsaid second mentioned means thereafter operative to progressivelyseparate said cylinders and pistons as they move by said ports and tofinally separate them beyond said ports.

13. In a compressor turbine, a stationary casing, a first elementrotatably mounted in said casing and having means at its outer peripheryfor cooperation with the casing to define a plurality of cylindersmovable with the element as the latter is rotated, a second elementrotatively mounted in said casing and at its outer periphery carrying aplurality of pistons for cooperation with said cylinders, meansconnecting said elements together'for rotation as a unit, an annularfiange on said casing and defining a portion of a wall of each of saidcylinders, turbine blades at the outer side of said flange and fast,

to one of said elements, a firing station, means whereby the respectivepistons and cylinders of the elements are telescoped at said station andseparate beyond said station as said elements rotate, and ports in saidflange beyond said station and through which the ignited expandingproducts of combustion may escape from the cylinders and impinge on saidturbine blades.

14. In a compressor turbine, a rotary multicylinder construction and arotary multi-piston construction, turbine blades rotatable with one ofsaid construction, means for compressing fuel by centrifugal action andsupplying it to the cylinders of said multi-cylinder construction andthereafter mechanically compressing it by telescoping of the respectivecylinders and pistons of said constructions, means for firing thecharges in the respective cylinders while the cylinders and pistons aretelescoped at a predetermined place in the path of rotation of theelements, and means for conducting the expanding products of combustionfrom said cylinders to said blades.

15. In a compressor turbine, a rotary multicylinder construction and arotary multi-piston construction, turbine blades rotatable with saidconstructions, means including impeller blades carried by opposing facesof said constructions for compressing fuel by centrifugal action andsupplying it to the cylinders of said multi-cylinder construction, meansfor thereafter telescoping the cylinder and pistons of saidconstructions to mechanically compress the fuel in said cylinders, meansfor firing the charges in the respective cylinders while the cylindersand pistons are telescoped and at a predetermined place in the path ofrotation of the elements, and means for directing the expanding productsof combustion from the cylinders to said turbine blades.

16. In a compressor turbine, a rotary multicylinder construction and arotary multi-piston construction, turbineblades rotatable with saidconstructions, means including impeller blades ca ried by one of saidconstructions ior comconstruction, means positively connecting turbineblades to one of said constructions, means for compressing fuel bycentrifugal action and supplying it to the cylinders of saidmulti-cylinder constructions, one of said constructions arranged at anangle to the other whereby for, a portion of a revolution the cylindersand pistons are moving into telescoping relation and for the otherportion they are separating whereby during the first mentioned portionof the revolution said fuel in the respective cylinders is being com;-pressed, means for firing the charges in the respective cylindersapproximately at the end of the first mentioned portion of therevolution 01' the constructions, and means for directing the expandingproducts of combustion from the cylinders to the blades.

18. In a compressor turbine, a pair of members, means mounting saidmembers for rotation together and for relative lateral movements, meansrotatable by one of said members to compress a fuel charge bycentrifugal action, means for further compressing said fuel charge by pitive mechanical compression on relative lateral movements of saidmembers, turbine blades in positive driving relation with one of saidmembers, means for igniting said fuel charge following compressionthereof on said relative lateral movements of said members, and meansfor impressing the ignited charge on said turbine blades.

19. In a compressor turbine, a pair of means ro- 12 tatable as a unitand of which one is movable toward and from the other while both arerotating, means for supp s a combustible charge to saidpair of means,impellers rotatable with said pair of means to compress said charge bycentrifugal action as the means of said pair rotate, other means tofurther compress said charge by mechanical action as said one means i ofsaid pair moves toward the other thereof, a

rotatable element carrying turbine blades, an igniter for the compressedcharge, and means for impressing the ignited charge on said turbineblades to impart rotation to said element.

20. In a compressor turbine, a pair of means rotatable as a unit and ofwhich one is movable toward and from the other while both are rotating,means for supplying a combustible charge to said pair of means,impellers rotatable with said pair of means to compress said charge bycentrifugal action as the means of said pair rotate, other means tofurther compress said charge by mechanical action as said one means ofsaid pair moves toward the other thereof, a rotatable element carryingturbine blades, an igniter for the compressed charge, means forimpressing the ignited charge on said turbine blades to impart rotationto said element, and said element rigid with one of the means of saidpair of means whereby as said element is rotated by said ignited chargeit causes rotation of said pair of means.

JOSEPH YOUHOUSE.

REFERENCES CITED The following references are of record in the file ofthis patent:

UNITED STATES PATENTS

